EP1965033A2 - Joint d'air externe de lames - Google Patents

Joint d'air externe de lames Download PDF

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Publication number
EP1965033A2
EP1965033A2 EP08250692A EP08250692A EP1965033A2 EP 1965033 A2 EP1965033 A2 EP 1965033A2 EP 08250692 A EP08250692 A EP 08250692A EP 08250692 A EP08250692 A EP 08250692A EP 1965033 A2 EP1965033 A2 EP 1965033A2
Authority
EP
European Patent Office
Prior art keywords
base portion
face
cavity
cover plate
aft
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP08250692A
Other languages
German (de)
English (en)
Other versions
EP1965033B1 (fr
EP1965033A3 (fr
Inventor
Edward F. Pietraszkiewicz
Joseph A. Peto
John C. Calderbank
Lisa P. O'neill
Michael J. Bruskotter
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP1965033A2 publication Critical patent/EP1965033A2/fr
Publication of EP1965033A3 publication Critical patent/EP1965033A3/fr
Application granted granted Critical
Publication of EP1965033B1 publication Critical patent/EP1965033B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/95—Preventing corrosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • the disclosure relates to gas turbine engines. More particularly, the disclosure relates to casting of cooled shrouds or blade outer air seals (BOAS).
  • BOAS blade outer air seals
  • BOAS segments may be internally cooled by bleed air.
  • cooling air may be fed into a plenum at the outboard or outside diameter (OD) side of the BOAS.
  • the cooling air may pass through passageways in the seal body and exit outlet ports in the inboard or inner diameter (ID) side of the body (e.g. to film cool the ID face).
  • Air may also exit along the circumferential ends (matefaces) of the BOAS so as to be vented into the adjacent inter-segment region (e.g., to help cool feather seal segments sealing the adjacent BOAS segments).
  • An exemplary BOAS configuration includes a casting and an OD cover plate welded to the casting. Air passes from the plenum through holes in the cover plate and into one or more feed chambers/cavities in the BOAS from which the passageways extend.
  • An exemplary BOAS is found in US Patent 6,393,331 .
  • a turbine engine blade outer air seal segment having a body having a base portion.
  • the base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges.
  • the body has at least one mounting hook.
  • At least one cover plate is secured to the body to define at least one cavity.
  • the cover plate has a plurality of feed holes.
  • a plurality of outlet holes extend through the base portion to the ID face.
  • At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating forward and aft cavity portions.
  • FIG. 1 shows blade outer air seal (BOAS) 20.
  • the BOAS has a main body portion 22 having a leading/upstream/forward end 24 and a trailing/downstream/aft end 26.
  • FIG. 1 further shows an approximate longitudinal/overall-downstream/aftward direction 500, an approximate radial outward direction 502, and an approximate circumferential direction 504.
  • the body has first and second circumferential ends or matefaces 28 and 30.
  • the body has an inner diameter (ID)/inboard face 32 and an outer diameter (OD)/outboard face 34.
  • the exemplary BOAS has a plurality of mounting hooks.
  • the exemplary BOAS has a single forward mounting hook 42 having a forwardly-projecting distal portion recessed aft of the forward end 24.
  • the exemplary BOAS has a series of four aft hooks 44 each having a rearwardly-projecting distal portion protruding beyond the aft end 26.
  • the BOAS has a wall structure 46 circumscribing/surrounding a recess/cavity 48 described in further detail below.
  • the exemplary distal portion of the forward hook 42 is formed as a full width lip extending from a front segment of the wall 46 ( FIG. 3 ).
  • the exemplary proximal portions of the aft hooks 44 extend upward from an aft segment of the wall 46.
  • a floor or base 50 of the chamber is locally formed by a central portion of the OD face 34.
  • the ID face may bear a thermal barrier coating 52 having an exposed surface 54.
  • a circumferential ring array of a plurality of the BOAS 20 may encircle an associated blade stage of a gas turbine engine.
  • the assembled ID faces 32/coating surfaces 54 thus locally bound an outboard extreme of the core flowpath 56 ( FIG. 3 ).
  • the BOAS 20 may have features for interlocking the array.
  • the exemplary matefaces 28 and 30 have complementary shiplap features.
  • Other implementations may include slots (not shown) for accommodating edges of seals spanning junctions between adjacent BOAS 20 or may include finger joints.
  • the BOAS may be air-cooled.
  • bleed air may be directed to a chamber 58 ( FIG. 3 ) immediately outboard of a baffle plate 60 that extends across the chamber 48.
  • a perimeter portion of the underside of the baffle plate 60 may sit atop and be welded or brazed to a shoulder surface 62 of the wall 46.
  • the bleed air may be directed through impingement feed holes 64 in the plate 60 to the inboard portion of the chamber 48.
  • Air may exit the chamber 48 through discharge passageways 70.
  • Exemplary passageways 70 extend from inlets 72 at the chamber 48 to outlets 74 along the TBC 52.
  • the exemplary casting includes a circumferential rib 80 in the chamber 48.
  • the exemplary rib is full shoulder height so that its outboard surface 82 may contact the underside/ID surface of the plate (e.g., and be secured thereto as the plate is secured to the shoulder surface 62).
  • the rib divides the portion of the chamber 48 below the plate 60 into a fore (sub)chamber/cavity 90 and an aft (sub)chamber/cavity 92.
  • the casting with full height rib 80 may represent a baseline prior art casting.
  • FIG. 3 schematically shows a blade 100 of the associated stage.
  • the blade has an airfoil with a leading edge 102, a trailing edge 104, and a tip 106.
  • Action of the airfoil imposes a pressure gradient to the airflow 520 passing downstream along the surface 54.
  • the gradient may provide an exemplary 50% drop in pressure from a leading group of the outlets 74 to a trailing group of the outlets 74.
  • This pressure difference may pose difficulties in cooling the BOAS.
  • feeding from a common chamber 48 may end up providing one or both of excessive flow through the trailing holes and insufficient flow through the leading holes.
  • the prior art has tailored the distribution of feed air to the two fully isolated chambers 90 and 92. Nevertheless, there remain such flow problems within either of the two chambers.
  • the chamber 92 is divided into separate upstream and downstream regions 120 and 122 respectively.
  • the division is only partial, with an open gap or restricted region 124 separating the regions 120 and 122 from each other.
  • the exemplary restriction is formed by a channel 130 in the baffle plate 60 projecting as a blister toward the floor 50.
  • the exemplary channel is essentially full width of the chamber 48 and provides the restricted region 124 with a height H 2 approximately 30-60% of a height H 1 of remaining majority portions of the chamber 92.
  • Exemplary heights are essentially uniform, but may also represent other characteristic heights (e.g., mean, modal, or median).
  • the exemplary chamber 92 has a length L 1 .
  • the center of the exemplary channel 130 is at a length L 2 downstream of the downstream face of the wall/rib 80.
  • Exemplary L 2 is 40-60% of L 1 .
  • an exemplary pressure in the flowpath 56 at the leading group of outlets 74 is an exemplary 300-400 psia (2.07-2.76 MPaa)whereas the pressure at a trailing/downstream group is about 50-75% of that.
  • Four upstream-to-downstream groups of holes 70 are fed from the cavity 90.
  • An exemplary pressure at the outlets 74 of the downstreammost of these four is proportionately less than at the leading group.
  • the size/number/distribution of holes along the cavity 90 may be selected to provide a pressure in the cavity 90 above that of the leading group of holes (e.g., 5-15% above or about 20-40psi (138-276 kPa)above).
  • the height H 2 is selected to be sufficiently small to permit an effective pressure difference between the regions 120 and 122.
  • the pressure difference allows each of the regions 120 and 122 to be maintained at an associated pressure above (e.g., 5-15% above) that of their highest pressure outlets 74.
  • the position of the channel may be selected to apportion the holes 70 between the regions 120 and 122 in such a way as to minimize total air requirements for a given cooling level.
  • H 2 might interfere with local cooling and might permit rubbing between the plate and body. Thus a higher value may be preferred.
  • Plate hole diameter for holes 64 (if any) and the quantity/distribution of such holes may be chosen in combination with H 2 to provide desired local impingement cooling.
  • the quantities of the holes 64 along each region 120 and 122 may be chosen to maintain the desired pressures in those regions.
  • FIG. 4 shows an alternative BOAS 220 otherwise similar but wherein the baffle plate 222 is unchanneled and a partial height rib 224 extends radially outward from the floor 50 to provide a restricted region 226.
  • the rib may be sized and positioned according to similar considerations as those used to size and position the channel.
  • the BOAS may be formed as a reengineering of a baseline BOAS configuration.
  • the shape of the casting is preserved while the channel 130 is added to an otherwise flat baffle plate.
  • Such a solution may, for example, have an advantage in that the wax pattern molded for the casting need not be altered. Stamping the channel into the sheetmetal baffle plate may be a much easier and less expensive solution.
  • the reengineering may also shift the distribution of the holes 64.
  • the hole size e.g., diameter for typical circular holes
  • Total hole area may be reduced to reduce total air consumption.
  • hole count may be reduced along the aft camber 92 and, more particularly, its aft region 122. More complex reengineerings might involve the holes 70.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08250692.4A 2007-03-01 2008-02-29 Joint d'air externe de lames Active EP1965033B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/712,812 US8439629B2 (en) 2007-03-01 2007-03-01 Blade outer air seal

Publications (3)

Publication Number Publication Date
EP1965033A2 true EP1965033A2 (fr) 2008-09-03
EP1965033A3 EP1965033A3 (fr) 2013-11-20
EP1965033B1 EP1965033B1 (fr) 2015-03-25

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Family Applications (1)

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EP08250692.4A Active EP1965033B1 (fr) 2007-03-01 2008-02-29 Joint d'air externe de lames

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US (1) US8439629B2 (fr)
EP (1) EP1965033B1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2224167A1 (fr) * 2009-02-25 2010-09-01 Siemens Aktiengesellschaft Carter de turbine à gaz
EP2479385A3 (fr) * 2011-01-25 2014-07-30 United Technologies Corporation Ensemble et support de joint d'air externe d'aubes
EP2835500A1 (fr) * 2013-08-09 2015-02-11 Siemens Aktiengesellschaft Elément d'insertion et turbine à gaz
EP3103967A1 (fr) * 2015-06-10 2016-12-14 United Technologies Corporation Joint d'air extérieur d'aube à revêtement partiel
EP2414639B1 (fr) 2009-03-30 2016-12-28 ALSTOM Technology Ltd Elément refroidi pour une turbine à gaz
US9995165B2 (en) 2011-07-15 2018-06-12 United Technologies Corporation Blade outer air seal having partial coating
EP2514925A3 (fr) * 2011-04-18 2019-06-26 General Electric Company Système de fixation d'une virole composite à matrice céramique
EP3599347A1 (fr) * 2018-07-23 2020-01-29 United Technologies Corporation Bloc de fixation pour joint d'air externe de lame assurant un refroidissement par impact
US10968772B2 (en) * 2018-07-23 2021-04-06 Raytheon Technologies Corporation Attachment block for blade outer air seal providing convection cooling
US11193386B2 (en) 2016-05-18 2021-12-07 Raytheon Technologies Corporation Shaped cooling passages for turbine blade outer air seal

Families Citing this family (45)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8123466B2 (en) * 2007-03-01 2012-02-28 United Technologies Corporation Blade outer air seal
US8439639B2 (en) * 2008-02-24 2013-05-14 United Technologies Corporation Filter system for blade outer air seal
US8740551B2 (en) * 2009-08-18 2014-06-03 Pratt & Whitney Canada Corp. Blade outer air seal cooling
US8714911B2 (en) * 2011-01-06 2014-05-06 General Electric Company Impingement plate for turbomachine components and components equipped therewith
US9062558B2 (en) 2011-07-15 2015-06-23 United Technologies Corporation Blade outer air seal having partial coating
US8826668B2 (en) * 2011-08-02 2014-09-09 Siemens Energy, Inc. Two stage serial impingement cooling for isogrid structures
EP2574732A2 (fr) * 2011-09-29 2013-04-03 Hitachi Ltd. Turbine à gaz
US20140064969A1 (en) * 2012-08-29 2014-03-06 Dmitriy A. Romanov Blade outer air seal
US9371735B2 (en) * 2012-11-29 2016-06-21 Solar Turbines Incorporated Gas turbine engine turbine nozzle impingement cover
EP2961930B1 (fr) 2013-02-26 2020-05-27 United Technologies Corporation Traitement des bords pour joint d'étanchéité à l'air externe d'aube
EP3030754B1 (fr) 2013-08-06 2018-11-14 United Technologies Corporation Joint étanche à l'air extérieur pour aube pourvu d'une caractéristique de charge radiale
WO2015031764A1 (fr) * 2013-08-29 2015-03-05 United Technologies Corporation Joint d'étanchéité à air externe à lame réalisé en un composite à matrice céramique
EP3042045A4 (fr) * 2013-09-06 2017-06-14 United Technologies Corporation Géométrie entre segments de boas incliné
US9206700B2 (en) * 2013-10-25 2015-12-08 Siemens Aktiengesellschaft Outer vane support ring including a strong back plate in a compressor section of a gas turbine engine
US10309255B2 (en) 2013-12-19 2019-06-04 United Technologies Corporation Blade outer air seal cooling passage
US20150285081A1 (en) * 2014-04-04 2015-10-08 United Technologies Corporation Gas turbine engine component with flow separating rib
US10774655B2 (en) 2014-04-04 2020-09-15 Raytheon Technologies Corporation Gas turbine engine component with flow separating rib
US9938846B2 (en) * 2014-06-27 2018-04-10 Rolls-Royce North American Technologies Inc. Turbine shroud with sealed blade track
US9945256B2 (en) 2014-06-27 2018-04-17 Rolls-Royce Corporation Segmented turbine shroud with seals
EP3029414A1 (fr) * 2014-12-01 2016-06-08 Siemens Aktiengesellschaft Aube de turbine, son procédé de fabrication et procédé de détermination de la situation d'un noyau utilisé lors de la coulée d'une aube de turbine
US9771814B2 (en) 2015-03-09 2017-09-26 United Technologies Corporation Tolerance resistance coverplates
US10107307B2 (en) * 2015-04-14 2018-10-23 Pratt & Whitney Canada Corp. Gas turbine engine rotor casing treatment
US9869201B2 (en) * 2015-05-29 2018-01-16 General Electric Company Impingement cooled spline seal
US9951634B2 (en) * 2015-06-11 2018-04-24 United Technologies Corporation Attachment arrangement for turbine engine component
EP3118420A1 (fr) * 2015-07-15 2017-01-18 Siemens Aktiengesellschaft Élément de paroi pouvant être refroidi avec plaque de refroidissement par impact
GB201514363D0 (en) * 2015-08-13 2015-09-30 Rolls Royce Plc Panel for lining a gas turbine engine fan casing
US10526897B2 (en) 2015-09-30 2020-01-07 United Technologies Corporation Cooling passages for gas turbine engine component
US10563534B2 (en) 2015-12-02 2020-02-18 United Technologies Corporation Blade outer air seal with seal arc segment having secondary radial supports
US10513943B2 (en) * 2016-03-16 2019-12-24 United Technologies Corporation Boas enhanced heat transfer surface
US10329941B2 (en) 2016-05-06 2019-06-25 United Technologies Corporation Impingement manifold
US10352789B2 (en) * 2017-02-09 2019-07-16 Microsoft Technology Licensing, Llc Measuring strain on display device
US11225880B1 (en) 2017-02-22 2022-01-18 Rolls-Royce Corporation Turbine shroud ring for a gas turbine engine having a tip clearance probe
US10900378B2 (en) 2017-06-16 2021-01-26 Honeywell International Inc. Turbine tip shroud assembly with plural shroud segments having internal cooling passages
US10677084B2 (en) 2017-06-16 2020-06-09 Honeywell International Inc. Turbine tip shroud assembly with plural shroud segments having inter-segment seal arrangement
CN110779042B (zh) * 2018-07-31 2021-02-26 中国人民解放军国防科技大学 旋转爆震燃烧室及具有其的发动机
US10822964B2 (en) 2018-11-13 2020-11-03 Raytheon Technologies Corporation Blade outer air seal with non-linear response
US10934941B2 (en) * 2018-11-19 2021-03-02 Raytheon Technologies Corporation Air seal interface with AFT engagement features and active clearance control for a gas turbine engine
US10920618B2 (en) 2018-11-19 2021-02-16 Raytheon Technologies Corporation Air seal interface with forward engagement features and active clearance control for a gas turbine engine
US11248482B2 (en) * 2019-07-19 2022-02-15 Raytheon Technologies Corporation CMC BOAS arrangement
US11274566B2 (en) * 2019-08-27 2022-03-15 Raytheon Technologies Corporation Axial retention geometry for a turbine engine blade outer air seal
US11525401B2 (en) * 2021-01-11 2022-12-13 Honeywell International Inc. Impingement baffle for gas turbine engine
US20230184118A1 (en) * 2021-12-14 2023-06-15 Solar Turbines Incorporated Turbine tip shroud removal feature
GB202216827D0 (en) * 2022-11-11 2022-12-28 Rolls Royce Plc A method of manufacturing a turbine component
US12467629B1 (en) * 2025-01-15 2025-11-11 Rtx Corporation CMC component with cover plate
US12613034B1 (en) * 2025-01-29 2026-04-28 Rtx Corporation Ceramic matrix composite component with corrugated wall

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6393331B1 (en) 1998-12-16 2002-05-21 United Technologies Corporation Method of designing a turbine blade outer air seal

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3603599A (en) * 1970-05-06 1971-09-07 Gen Motors Corp Cooled seal
US4314792A (en) * 1978-12-20 1982-02-09 United Technologies Corporation Turbine seal and vane damper
US4487016A (en) * 1980-10-01 1984-12-11 United Technologies Corporation Modulated clearance control for an axial flow rotary machine
US4526226A (en) * 1981-08-31 1985-07-02 General Electric Company Multiple-impingement cooled structure
FR2724973B1 (fr) * 1982-12-31 1996-12-13 Snecma Dispositif d'etancheite d'aubages mobiles de turbomachine avec controle actif des jeux en temps reel et methode de determination dudit dispositif
US4553901A (en) * 1983-12-21 1985-11-19 United Technologies Corporation Stator structure for a gas turbine engine
US4642024A (en) * 1984-12-05 1987-02-10 United Technologies Corporation Coolable stator assembly for a rotary machine
US4688988A (en) * 1984-12-17 1987-08-25 United Technologies Corporation Coolable stator assembly for a gas turbine engine
US5048288A (en) * 1988-12-20 1991-09-17 United Technologies Corporation Combined turbine stator cooling and turbine tip clearance control
US5092735A (en) * 1990-07-02 1992-03-03 The United States Of America As Represented By The Secretary Of The Air Force Blade outer air seal cooling system
US5649806A (en) * 1993-11-22 1997-07-22 United Technologies Corporation Enhanced film cooling slot for turbine blade outer air seals
US5609469A (en) 1995-11-22 1997-03-11 United Technologies Corporation Rotor assembly shroud
FR2766517B1 (fr) * 1997-07-24 1999-09-03 Snecma Dispositif de ventilation d'un anneau de turbomachine
US6139257A (en) * 1998-03-23 2000-10-31 General Electric Company Shroud cooling assembly for gas turbine engine
US6126389A (en) * 1998-09-02 2000-10-03 General Electric Co. Impingement cooling for the shroud of a gas turbine
JP4698847B2 (ja) * 2001-01-19 2011-06-08 三菱重工業株式会社 ガスタービン分割環
DE50210878D1 (de) * 2001-07-05 2007-10-25 Alstom Technology Ltd Verfahren zur Montage eines Prallblechs
US7033138B2 (en) * 2002-09-06 2006-04-25 Mitsubishi Heavy Industries, Ltd. Ring segment of gas turbine
US6997673B2 (en) * 2003-12-11 2006-02-14 Honeywell International, Inc. Gas turbine high temperature turbine blade outer air seal assembly
EP1990507B1 (fr) * 2006-03-02 2015-04-15 IHI Corporation Structure de refroidissement par contact

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6393331B1 (en) 1998-12-16 2002-05-21 United Technologies Corporation Method of designing a turbine blade outer air seal

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2224167A1 (fr) * 2009-02-25 2010-09-01 Siemens Aktiengesellschaft Carter de turbine à gaz
EP2414639B1 (fr) 2009-03-30 2016-12-28 ALSTOM Technology Ltd Elément refroidi pour une turbine à gaz
EP2479385A3 (fr) * 2011-01-25 2014-07-30 United Technologies Corporation Ensemble et support de joint d'air externe d'aubes
US10077680B2 (en) 2011-01-25 2018-09-18 United Technologies Corporation Blade outer air seal assembly and support
EP2514925A3 (fr) * 2011-04-18 2019-06-26 General Electric Company Système de fixation d'une virole composite à matrice céramique
US9995165B2 (en) 2011-07-15 2018-06-12 United Technologies Corporation Blade outer air seal having partial coating
CN105452607A (zh) * 2013-08-09 2016-03-30 西门子股份公司 插入件、环段、燃气涡轮机、安装方法
CN105452607B (zh) * 2013-08-09 2017-11-10 西门子股份公司 燃气涡轮机及安装方法
US10047626B2 (en) 2013-08-09 2018-08-14 Siemens Aktiengesellschaft Gas turbine and mounting method
WO2015018841A1 (fr) * 2013-08-09 2015-02-12 Siemens Aktiengesellschaft Élément rapporté, segment annulaire, turbine à gaz, procédé de montage
EP2835500A1 (fr) * 2013-08-09 2015-02-11 Siemens Aktiengesellschaft Elément d'insertion et turbine à gaz
EP3103967A1 (fr) * 2015-06-10 2016-12-14 United Technologies Corporation Joint d'air extérieur d'aube à revêtement partiel
US11193386B2 (en) 2016-05-18 2021-12-07 Raytheon Technologies Corporation Shaped cooling passages for turbine blade outer air seal
EP3246533B1 (fr) * 2016-05-18 2023-06-28 Raytheon Technologies Corporation Passages de refroidissement formés pour joint d'air extérieur d'aube de turbine
EP3599347A1 (fr) * 2018-07-23 2020-01-29 United Technologies Corporation Bloc de fixation pour joint d'air externe de lame assurant un refroidissement par impact
US10961866B2 (en) 2018-07-23 2021-03-30 Raytheon Technologies Corporation Attachment block for blade outer air seal providing impingement cooling
US10968772B2 (en) * 2018-07-23 2021-04-06 Raytheon Technologies Corporation Attachment block for blade outer air seal providing convection cooling

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US8439629B2 (en) 2013-05-14
EP1965033B1 (fr) 2015-03-25
EP1965033A3 (fr) 2013-11-20
US20090067994A1 (en) 2009-03-12

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